Radar sensor concept for multi-sensor missile applications

Abstract

Disclosed is an antenna array for detecting and/or tracking one or more objects. The antenna array comprises a receiving antenna array having antenna elements for receiving a signal, wherein the receiving antenna array is arranged in a first one-dimensional array. The antenna array further comprises a transmitting antenna array having antenna elements for transmitting the signal, wherein the transmitting antenna array is arranged in a second one-dimensional array which is different from the first one-dimensional array.

1 . An antenna array for detecting and/or tracking one or more objects, wherein the antenna array comprises:
 a receiving antenna array (Rx 1  and/or Rx 2 ) comprising antenna elements ( 111  and/or  113 ) for receiving a signal, wherein the receiving antenna array (Rx 1  and/or Rx 2 ) is arranged in a first one-dimensional array;   a transmitting antenna array (Tx 1  and/or Tx 2 ) comprising antenna elements ( 112  and/or  114 ) for transmitting the signal, wherein the transmitting antenna array (Tx 1  and/or Tx 2 ) is arranged in a second one-dimensional array which is different from the first one-dimensional array.   
     
     
         2 . The antenna array according to  claim 1 ,
 wherein the first one-dimensional array has a shape of an edge of a control surface of a missile ( 100 ;  200 ), preferably being a linear array; and/or   wherein the second one-dimensional array has the shape of an edge of a control surface of the missile ( 100 ;  200 ), preferably being a linear array.   
     
     
         3 . The antenna array according to  claim 1 , wherein the first one-dimensional array and the second one-dimensional array form an angle in the range between 45° and 135°, preferably orthogonal to each other. 
     
     
         4 . The antenna array according to  claim 1 , wherein the antenna array comprises the receiving antenna array and the transmitting antenna array. 
     
     
         5 . The antenna array according to  claim 1 ,
 wherein the receiving antenna array comprises a first plurality (Rx 1 ) of antenna elements ( 111 ) and a third plurality (Rx 2 ) of antenna elements ( 113 ); and/or   wherein the transmitting antenna array comprises a second plurality (Tx 1 ) of antenna elements ( 112 ) and a fourth plurality (Tx 2 ) of antenna elements ( 114 ).   
     
     
         6 . The antenna array according to  claim 1 ,
 wherein the antenna elements ( 112  and/or  114 ) of the transmitting antenna array (Tx 1  and/or Tx 2 ) are configurable to transmit phase-synchronized signals to generate a common directional antenna lobe; and/or   wherein the antenna elements ( 112  and/or  114 ) of the transmitting antenna array (Tx 1  and/or Tx 2 ) are configurable to transmit orthogonal signals in pairs.   
     
     
         7 . A missile ( 100 ;  200 ), wherein the missile ( 100 ;  200 ) comprises:
 a plurality ( 110 ;  210 ,  220 ) of control surfaces; and   the antenna array according to  claim 1 ;   wherein the receiving antenna array (Rx 1  and/or Rx 2 ) and the transmitting antenna array (Tx 1  and/or Tx 2 ) are arranged on different control surfaces of the plurality ( 110 ;  210 ,  220 ) of control surfaces.   
     
     
         8 . The missile ( 100 ;  200 ) according to  claim 7 , wherein the missile ( 100 ;  200 ) further comprises an infrared sensor for detecting and/or tracking the object. 
     
     
         9 . The missile ( 100 ;  200 ) according to  claim 7 ,
 wherein the first plurality (Rx 1 ) of antenna elements ( 111 ) is arranged on an edge of a first control surface;   wherein the second plurality (Tx 1 ) of antenna elements ( 112 ) is arranged on an edge of a second control surface;   wherein the third plurality (Rx 2 ) of antenna elements ( 113 ) is arranged on an edge of a third control surface; and   wherein the fourth plurality (Tx 2 ) of antenna elements ( 114 ) is arranged on an edge of a fourth control surface.   
     
     
         10 . The missile ( 100 ;  200 ) according to  claim 7 , wherein the control surfaces of the plurality ( 110 ;  210 ,  220 ) of control surfaces can be folded out in a telescopic manner, by rotating about an axis (z) in the flight direction of the missile ( 100 ;  200 ), or about an axis orthogonal to the flight direction, and preferably have a thickness of five millimeters or less.